Exergetic effects of some design parameters on the small turbojet engine for unmanned air vehicle applications

This article analyses some design parameters on the exergetic and energetic performances for a small turbojet engine for unmanned vehicles. On the basis of theoretical data employed, some exergetic and aerothermodynamics aspects of the engine and its components are parametrically studied in terms of compressor pressure ratio (πc) and turbine inlet temperature (Tt4). The results show that mainly based on the operating parameters for 2<πc < 7, 1200 K < Tt4 < 1500 K and thrust range values are in the range of 894–907 N, increasing turbine inlet temperature decreases the exergy efficiency of the small turbojet engine. However, any increase in compressor pressure ratio along with increase in flight Mach number results in an increasing exergy efficiency of the engine. Computer experiments were performed at 9000 m altitude with flight Mach number of 0.8 and 0.9. Studying these parameters indicates how much improvement is possible for the small turbojet engine to achieve better energy and exergy consumption.

► Evaluating the effects of some design parameters on the exergetic performance of a small turbojet engine.
► Turbojet engine exergetic evaluation related to compressor aerodynamic and combustor material properties.
► Determining the exergy efficiencies on a small turbojet engine components used in unmanned air vehicles.
► Any increase in compressor pressure ratio along with results in an increasing exergy efficiency of the engine.